Fatigue crack location and fatigue life for riveted lap joints in aircraft fuselage

Author:

Skorupa A.,Skorupa M.,Machniewicz T.,Korbel A.

Publisher

Elsevier BV

Subject

Industrial and Manufacturing Engineering,Mechanical Engineering,Mechanics of Materials,General Materials Science,Modeling and Simulation

Reference17 articles.

1. Airframe structural design;Niu,1988

2. Airframe stress analysis and sizing;Niu,1999

3. Vlieger H. Results of uniaxial and biaxial tests on riveted fuselage lap joint specimens. In: Proceedings of the FAA/NASA international symposium of advanced structural integrity methods for airframe durability and damage tolerance, 4–6 May, Hampton, VA, USA, NASA CP, vol. 3274; 1994, p. 911–30.

4. Vlieger H, Ottens HH. Uniaxial and biaxial tests on riveted fuselage lap joint specimens, Report NLR CR 97319 L. Amsterdam: NLR; 1998.

5. Hartman A. Fatigue tests on single lap joints in clad 2024-T3 aluminium alloy manufactured by a combination of riveting and adhesive bonding, Report NLR M.2170. Amsterdam: NLR; 1966.

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